Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(goe758-il) GOE 758 AIRFOIL | Gottingen 758 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe758-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe758-il | 50,000 | 9 | 7.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 50,000 | 5 | 25.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 9 | 45.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 5 | 52.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 9 | 73.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 9 | 108.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 5 | 102.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 9 | 133.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 5 | 123.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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